NREL's S812 Airfoil (s812-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S812 Airfoil (s812-nr) Reynolds number: 200,000 Max Cl/Cd: 59.65 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s812-nr-200000-n5.txt Download as CSV file: xf-s812-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S812 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5503 0.09873 0.09475 -0.0686 1.0000 0.0132
-14.250 -0.5714 0.09319 0.08911 -0.0700 1.0000 0.0130
-14.000 -0.5919 0.08819 0.08400 -0.0709 1.0000 0.0130
-13.750 -0.6134 0.08341 0.07910 -0.0712 1.0000 0.0129
-13.500 -0.6324 0.07922 0.07479 -0.0711 1.0000 0.0128
-13.250 -0.6505 0.07532 0.07076 -0.0706 1.0000 0.0128
-13.000 -0.6680 0.07154 0.06683 -0.0697 1.0000 0.0127
-12.750 -0.6768 0.06706 0.06215 -0.0706 0.9952 0.0127
-12.500 -0.6796 0.06262 0.05747 -0.0721 0.9860 0.0127
-12.250 -0.6776 0.05809 0.05266 -0.0736 0.9754 0.0129
-11.750 -0.6469 0.04951 0.04335 -0.0764 0.9219 0.0135
-11.250 -0.5540 0.04312 0.03601 -0.0886 0.8259 0.0155
-11.000 -0.5264 0.04172 0.03428 -0.0894 0.7972 0.0161
-10.750 -0.4889 0.04056 0.03279 -0.0895 0.7799 0.0168
-10.500 -0.4501 0.03997 0.03190 -0.0892 0.7672 0.0178
-10.250 -0.4178 0.03967 0.03135 -0.0886 0.7572 0.0186
-10.000 -0.3908 0.03946 0.03108 -0.0881 0.7486 0.0198
-9.750 -0.3692 0.03908 0.03065 -0.0876 0.7415 0.0209
-9.500 -0.3464 0.03884 0.03033 -0.0869 0.7350 0.0220
-9.250 -0.3231 0.03877 0.03016 -0.0859 0.7297 0.0230
-9.000 -0.3026 0.03854 0.02985 -0.0850 0.7248 0.0239
-8.750 -0.2848 0.03812 0.02937 -0.0841 0.7199 0.0247
-8.500 -0.2714 0.03752 0.02878 -0.0830 0.7154 0.0262
-8.250 -0.2581 0.03679 0.02802 -0.0822 0.7117 0.0275
-8.000 -0.2462 0.03595 0.02716 -0.0813 0.7077 0.0284
-7.750 -0.2362 0.03497 0.02614 -0.0804 0.7043 0.0293
-7.500 -0.2278 0.03388 0.02497 -0.0794 0.7011 0.0304
-7.250 -0.2204 0.03274 0.02375 -0.0783 0.6983 0.0315
-7.000 -0.2184 0.03134 0.02230 -0.0770 0.6957 0.0330
-6.750 -0.2151 0.03000 0.02094 -0.0756 0.6928 0.0344
-6.500 -0.2100 0.02879 0.01968 -0.0743 0.6901 0.0361
-6.250 -0.2050 0.02759 0.01841 -0.0729 0.6874 0.0378
-6.000 -0.1990 0.02646 0.01718 -0.0716 0.6850 0.0396
-5.750 -0.1954 0.02522 0.01586 -0.0700 0.6826 0.0425
-5.500 -0.1902 0.02408 0.01467 -0.0685 0.6803 0.0465
-5.250 -0.1864 0.02289 0.01345 -0.0667 0.6777 0.0542
-5.000 -0.1880 0.02151 0.01209 -0.0644 0.6752 0.0712
-4.750 -0.2037 0.01983 0.01051 -0.0605 0.6728 0.1097
-4.500 -0.2285 0.01695 0.00803 -0.0572 0.6705 0.2629
-4.250 -0.2282 0.01512 0.00702 -0.0558 0.6686 0.4542
-4.000 -0.2013 0.01526 0.00718 -0.0560 0.6669 0.4846
-3.750 -0.1728 0.01553 0.00741 -0.0564 0.6654 0.5011
-3.500 -0.1440 0.01611 0.00801 -0.0565 0.6635 0.5180
-3.250 -0.1153 0.01671 0.00860 -0.0566 0.6615 0.5291
-3.000 -0.0870 0.01697 0.00882 -0.0568 0.6594 0.5336
-2.750 -0.0599 0.01683 0.00858 -0.0574 0.6574 0.5364
-2.500 -0.0328 0.01658 0.00819 -0.0581 0.6556 0.5392
-2.250 -0.0046 0.01656 0.00811 -0.0585 0.6540 0.5406
-2.000 0.0237 0.01659 0.00811 -0.0590 0.6526 0.5418
-1.750 0.0521 0.01662 0.00810 -0.0595 0.6513 0.5433
-1.500 0.0807 0.01665 0.00809 -0.0600 0.6500 0.5449
-1.250 0.1083 0.01665 0.00808 -0.0604 0.6485 0.5468
-1.000 0.1356 0.01662 0.00804 -0.0609 0.6466 0.5488
-0.750 0.1631 0.01656 0.00795 -0.0614 0.6446 0.5511
-0.500 0.1910 0.01648 0.00780 -0.0621 0.6428 0.5538
-0.250 0.2190 0.01649 0.00782 -0.0626 0.6413 0.5553
0.000 0.2469 0.01655 0.00791 -0.0630 0.6398 0.5565
0.250 0.2751 0.01662 0.00799 -0.0634 0.6384 0.5580
0.500 0.3034 0.01668 0.00807 -0.0639 0.6371 0.5596
0.750 0.3321 0.01674 0.00813 -0.0645 0.6357 0.5616
1.000 0.3611 0.01679 0.00817 -0.0652 0.6344 0.5639
1.250 0.3884 0.01684 0.00824 -0.0657 0.6327 0.5664
1.500 0.4157 0.01688 0.00828 -0.0662 0.6310 0.5691
1.750 0.4425 0.01698 0.00846 -0.0665 0.6293 0.5705
2.000 0.4693 0.01709 0.00866 -0.0667 0.6275 0.5718
2.250 0.4964 0.01719 0.00884 -0.0669 0.6256 0.5733
2.500 0.5240 0.01729 0.00900 -0.0673 0.6239 0.5750
2.750 0.5519 0.01739 0.00916 -0.0678 0.6225 0.5769
3.000 0.5804 0.01748 0.00928 -0.0684 0.6210 0.5791
3.250 0.6096 0.01756 0.00938 -0.0691 0.6196 0.5816
3.500 0.6385 0.01766 0.00950 -0.0698 0.6181 0.5842
3.750 0.6621 0.01785 0.00984 -0.0695 0.6155 0.5858
4.000 0.6868 0.01802 0.01015 -0.0694 0.6129 0.5873
4.250 0.7128 0.01815 0.01040 -0.0694 0.6102 0.5889
4.500 0.7402 0.01821 0.01055 -0.0697 0.6075 0.5907
4.750 0.7694 0.01820 0.01060 -0.0703 0.6049 0.5927
5.000 0.7963 0.01824 0.01071 -0.0705 0.6014 0.5948
5.250 0.8188 0.01827 0.01087 -0.0699 0.5954 0.5972
5.500 0.8489 0.01800 0.01059 -0.0704 0.5897 0.5998
5.750 0.8706 0.01792 0.01067 -0.0695 0.5821 0.6013
6.000 0.8968 0.01767 0.01051 -0.0692 0.5747 0.6030
6.250 0.9175 0.01761 0.01061 -0.0681 0.5662 0.6047
6.500 0.9435 0.01737 0.01043 -0.0678 0.5580 0.6066
6.750 0.9616 0.01740 0.01063 -0.0663 0.5473 0.6087
7.000 0.9818 0.01735 0.01070 -0.0651 0.5351 0.6110
7.250 1.0005 0.01728 0.01071 -0.0637 0.5187 0.6134
7.500 1.0171 0.01724 0.01069 -0.0618 0.4949 0.6156
7.750 1.0277 0.01723 0.01058 -0.0587 0.4549 0.6171
8.000 1.0228 0.01765 0.01073 -0.0530 0.4054 0.6187
8.250 1.0125 0.01870 0.01152 -0.0472 0.3595 0.6204
8.500 1.0024 0.02002 0.01265 -0.0420 0.3202 0.6222
8.750 0.9932 0.02152 0.01401 -0.0375 0.2844 0.6242
9.000 0.9851 0.02321 0.01556 -0.0338 0.2527 0.6262
9.250 0.9795 0.02501 0.01724 -0.0310 0.2243 0.6281
9.500 0.9756 0.02692 0.01904 -0.0287 0.1979 0.6299
9.750 0.9732 0.02885 0.02089 -0.0267 0.1737 0.6316
10.000 0.9737 0.03068 0.02267 -0.0251 0.1515 0.6331
10.250 0.9754 0.03249 0.02443 -0.0237 0.1329 0.6349
10.500 0.9783 0.03427 0.02617 -0.0225 0.1166 0.6367
10.750 0.9830 0.03597 0.02785 -0.0215 0.1026 0.6386
11.000 0.9884 0.03766 0.02954 -0.0206 0.0908 0.6406
11.250 0.9952 0.03929 0.03118 -0.0199 0.0807 0.6426
11.500 1.0022 0.04094 0.03285 -0.0192 0.0724 0.6445
12.000 1.0162 0.04431 0.03628 -0.0180 0.0585 0.6482
12.250 1.0225 0.04610 0.03809 -0.0175 0.0526 0.6501
12.500 1.0310 0.04775 0.03979 -0.0172 0.0468 0.6522
12.750 1.0384 0.04955 0.04163 -0.0168 0.0422 0.6544
13.000 1.0473 0.05124 0.04342 -0.0166 0.0384 0.6566
13.250 1.0531 0.05330 0.04548 -0.0164 0.0351 0.6588
13.500 1.0631 0.05499 0.04729 -0.0163 0.0319 0.6611
13.750 1.0702 0.05696 0.04934 -0.0162 0.0290 0.6629
14.000 1.0759 0.05914 0.05159 -0.0161 0.0268 0.6648
14.250 1.0835 0.06117 0.05377 -0.0161 0.0245 0.6669
14.500 1.0890 0.06348 0.05616 -0.0162 0.0222 0.6694
14.750 1.0933 0.06600 0.05876 -0.0164 0.0203 0.6720
15.000 1.0987 0.06843 0.06132 -0.0166 0.0187 0.6747
15.250 1.1029 0.07108 0.06406 -0.0170 0.0171 0.6772
15.500 1.1050 0.07399 0.06709 -0.0174 0.0161 0.6795
15.750 1.1090 0.07677 0.07002 -0.0179 0.0147 0.6819
16.000 1.1123 0.07969 0.07306 -0.0186 0.0138 0.6845
16.250 1.1136 0.08294 0.07640 -0.0194 0.0131 0.6871
16.500 1.1134 0.08646 0.08004 -0.0203 0.0126 0.6898
16.750 1.1140 0.08997 0.08370 -0.0213 0.0120 0.6924
17.000 1.1140 0.09363 0.08753 -0.0225 0.0116 0.6948
17.250 1.1132 0.09746 0.09151 -0.0238 0.0112 0.6974
17.500 1.1121 0.10141 0.09561 -0.0253 0.0108 0.7004
17.750 1.1105 0.10552 0.09986 -0.0270 0.0106 0.7036
18.000 1.1077 0.10992 0.10439 -0.0289 0.0103 0.7070
18.250 1.1042 0.11448 0.10911 -0.0310 0.0101 0.7098
18.500 1.1007 0.11911 0.11388 -0.0332 0.0099 0.7131
18.750 1.0963 0.12392 0.11881 -0.0357 0.0098 0.7168
19.000 1.0925 0.12877 0.12384 -0.0382 0.0096 0.7205
19.250 1.0882 0.13377 0.12902 -0.0409 0.0095 0.7241
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